摘要
对HARIKA程序进行改进,创新性地修正了效率模型并引入Koch失速静压升系数模型,采用E3十级高压压气机气动特性试验数据验证此改进HARIKA程序,结果表明改进HARIKA程序对压气机100%转速失速边界的预估精度达到了99%。采用NSGA-II多目标遗传算法进行气动方案设计优化,优化后的方案与初始方案相比设计点的总效率提高了3.4%,喘振裕度提高了6%;通过调节进口导叶和前五级静子叶片的安装角,使得优化方案在非设计转速下的特性也得到了提高。
The efficiency models Firstly,was improved based on the HARIKA program.The stalling pressure rise method pro-posed by C.C.Koch was used to predict stall margin of axial flow compressors.Then,the modified program was applied to cal-culate the characteristic of a ten-stage compressor.The results show that the accuracy of predicting stall margin achieves 99%. Finally,the NSGA-II was used to optimize the overall aerodynamic design.After optimization,the compressor peak efficiency at the design rotational speed increase by 3.4% compared to the initial characters and its surge margin increase from 1 1.6% to 17.6%.The off-design performances also increase by optimizing the angles of both the inlet guide vanes and the former five vanes.The character lines of 90% design rotational speed shows a higher peak efficiency and surge margin after optimization the stator value.
出处
《流体机械》
CSCD
北大核心
2016年第6期24-28,16,共6页
Fluid Machinery
基金
国家自然科学基金项目(51576124)
2011先进航空发动机协同创新中心项目
关键词
高压压气机
气动方案设计
效率模型
可调静叶角度
优化
high pressure compressor
aerodynamic preliminary design
efficiency model
variable stator value
optimization
